Aircraft secondary power supply control circuit with emergency conversion function

Abstract

The invention belongs to the technical field of aircraft electrical systems, and relates to an aircraft secondary power supply control circuit with an emergency conversion function. Two single-phase static converters, two converter fault signal relays, an emergency conversion relay, a power supply control relay of electric equipment, a switch and a bus bar are designed to complete power supply, fault alarm and emergency conversion of a secondary power supply to an aircraft electrical system. The principle is simple and clear, implementation is convenient and feasible, connection and disconnection, fault warning and fault emergency conversion between the secondary power supply and the electric equipment can be achieved by adding the converter fault signal relay, the emergency conversion relay, the power supply control relays of the electric equipment and the switches, and the aircraft can be effectively protected after use, verification and flight test. It is indicated that the design principle is reliable and effective, power supply of important electric equipment can be guaranteed under the condition that the first converter or the second converter of the airplane breaks down, the reliability and safety of power supply of a secondary power source are improved, and the design principle is of great significance to flight safety.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft electrical systems and relates to an aircraft secondary power supply control circuit with an emergency conversion function. Background Art

[0002] The aircraft power system is used to provide various forms of electrical energy required by the onboard electrical equipment in all operating conditions of the aircraft, including main power supply, secondary power supply and emergency power supply.

[0003] The present invention relates to a power supply control circuit of an aircraft secondary power supply. The secondary power supply of a certain type of aircraft is composed of two single-phase static converters. The static converter converts the 28.5V DC power supply on board into 115V / 400Hz single-phase AC power to supply power to the single-phase AC power equipment on board. The No. 2 static converter is used to supply power to important power equipment in normal operation, and the No. 1 static converter is used as a backup of the No. 2 static converter to supply power to general power equipment. In the event of a failure of the No. 2 static converter, the system automatically converts the important equipment carried by the No. 2 static converter to be powered by the No. 1 static converter, and at the same time cuts off the power supply to the general power equipment under the No. 1 static converter, so as to realize the emergency conversion of the secondary power supply when the No. 2 static converter fails; when the main power supply system fails, the No. 1 static converter stops working. Summary of the invention

[0004] Through the design of this circuit, as long as one static converter works normally, the power supply of important electrical equipment can be guaranteed, which can effectively avoid the occurrence of aircraft power supply failure caused by static converter failure and improve the reliability of the system's secondary power supply.

[0005] Purpose of the Invention

[0006] The purpose of the present invention is to design a circuit for supplying power to an aircraft electrical system from a secondary power supply, the circuit having a fault alarm function and an emergency conversion function in case of a fault. When a static converter fails, general electrical equipment can be automatically cut off, emergency conversion can be made to a state capable of ensuring power supply to important equipment, and a fault signal can be issued. The design of the circuit improves the reliability of the aircraft's secondary power supply, avoids power outages of equipment due to secondary power supply failures, and improves the reliability and safety of the aircraft's secondary power supply.

[0007] Technical Solution

[0008] An aircraft secondary power supply control circuit with an emergency conversion function includes a No. 1 static converter X1, a No. 2 static converter X2, a No. 1 converter fault relay 5X, an emergency power conversion relay 6X, an important equipment B relay 7X, an emergency power conversion relay 8X, a No. 2 converter fault signal relay 9X, an important equipment A relay 10X, a general equipment C relay 12X, an important equipment D relay 13X, a general equipment A relay 14X, an important equipment C relay 15X, and a general equipment B relay 30X;

[0009] The direct current on the first bus is respectively connected to the A contact on the No. 1 converter fault relay 5X and the 3 contact on the No. 1 static converter X1; the A contact on the No. 1 converter fault relay 5X is connected to the 5 contact, the B contact of the No. 1 converter fault relay 5X is connected to the 7 contact of the No. 1 static converter X1, and the 2 contact and the 8 contact on the No. 1 static converter X1 are grounded; the No. 1 contact on the No. 1 static converter X1 is connected to the No. 2 contact of the emergency power supply transfer relay 6X, the No. 9 contact of the No. 1 static converter X1 is connected to the No. 4 contact of the emergency power supply transfer relay 6X, and the No. 10 contact of the No. 1 static converter X1 is connected to the No. 5 contact of the emergency power supply transfer relay 6X;

[0010] The A contact of the emergency power supply transfer relay 6X is connected to the power supply, the B contact is grounded, the 5 contact is connected to the 1 contact of the general equipment A relay 14X, the 4 contact is connected to the 5 contact of the general equipment C relay 12X, the 3 contact is connected to the 3 contact of the emergency power supply transfer relay 8X, and the 2 contact is connected to the 5 contact of the emergency power supply transfer relay 8X;

[0011] The A contact of the general equipment A relay 14X is connected to the second bus bar after passing through the first switch, the B contact is grounded, the 2 contact is connected to the 5 contact of the general equipment B relay 30X, the 6 contact is connected to the 4 contact of the emergency power supply conversion relay 8X in one way, and the 2 contact of the general equipment B relay 30X in the other way, and the 5 contact is connected to the general equipment A;

[0012] The A contact of the general device B relay 30X is connected to the second bus bar through the second switch, the B contact is grounded, the 4 contact is connected to the 4 contact of the general device C relay 12X, the 2 contact is connected to the 3 contact of the general device C relay 12X, and the 3 contact is connected to the general device B;

[0013] The A contact of the general equipment C relay 12X is connected to the first switch, the B contact is grounded, the 5 contact is connected to the 4 contact of the emergency power supply switching relay 6X, and the 2 contact is connected to the general equipment C;

[0014] Contact 1 of No. 2 static converter X2 is connected to contact 1 of emergency power supply transfer relay 8X, contact 2 is grounded, contact 3 is connected to the first bus, contact 6 is connected to the first bus, contact 7 is connected to contact B of No. 2 converter fault signal relay 9X, contact 8 is grounded, contact 9 is connected to contact 4 of important equipment D relay 13X, and contact 10 is connected to contact 5 of important equipment A relay 10X;

[0015] The A contact of the emergency power supply transfer relay 8X is connected to the 6 contact of the No. 2 converter fault signal relay 9X, the B contact is grounded, and the 2 contact is connected to the 2 contact of the important equipment A relay 10X;

[0016] The A contact of the No. 2 converter fault signal relay 9X is connected to the first bus bar, the A contact is connected to the 8 contact, and the 8 contact is connected to the 5 contact;

[0017] The A contact of the important equipment A relay 10X is connected to the third bus bar after passing through the third switch, the B contact is grounded, the 4 contact is connected to the 5 contact of the important equipment B relay 7X, the 2 contact is connected to the 2 contact of the important equipment B relay 7X, and the 3 contact is connected to the important equipment A;

[0018] The A contact of the important equipment B relay 7X is connected to the third bus bar after passing through the fourth switch, the B contact is grounded, the 4 contact is connected to the 4 contact of the important equipment C relay 15X, the 2 contact is connected to the 2 contact of the important equipment C relay 15X, and the 3 contact is connected to the important equipment B;

[0019] The A contact of the important equipment C relay 15X is connected to the third rear bar after passing through the fifth switch, and the B contact is grounded, and the B contact of the important equipment D relay 13X is connected in parallel. The 4 contact is connected to the 5 contact of the important equipment D relay 13X, the 2 contact is connected to the 2 contact of the important equipment D relay 13X; the 3 contact is connected to the important equipment C

[0020] Contact A of relay 13X of important equipment D is connected to the third bus bar through the fifth switch, and contact 3 is connected to important equipment D.

[0021] Furthermore, when the 9th and 10th pins of the No. 1 static converter X1 are turned on, both static converters are in a standby state. When the first or second switch under the No. 1 static converter X1 is turned on, the power control relay of the electrical equipment works.

[0022] Furthermore, the 9th and 10th pins of the No. 1 static converter X1 are disconnected, and the No. 1 static converter X1 converts the 28.5V DC power on the aircraft into 115V / 400Hz single-phase AC power, and outputs the AC power through the 1st pin of the static converter to supply power to the corresponding electrical equipment on the aircraft;

[0023] Further, when the No. 1 static converter X1 fails, the converter fault signal relay sends a fault signal to the onboard warning system upon receiving the fault signal sent from the 7th pin of the No. 1 static converter X1;

[0024] Furthermore, when the No. 2 static converter X2 fails, a fault signal is issued and the emergency power conversion relay 8X is activated; when the No. 2 static converter X2 fails, the system automatically switches the equipment carried by the No. 2 static converter X2 to the power supply of the No. 1 static converter X1 through the emergency power conversion relay 8X, and at the same time cuts off the power supply to the general electrical equipment under the No. 1 static converter X1.

[0025] Furthermore, when at least one of the first switch 1 and the second switch 2 is turned on, the corresponding general equipment A relay 14X or the general equipment B relay 30X or the general equipment C relay 12X works, and the remote control line pins 9 and 10 of the static converter X1 No. 1 change from the "closed" state to the "open" state, and the static converter X1 No. 1 outputs 115V / 400Hz single-phase AC power through pin 1.

[0026] Furthermore, pin 1 of static converter X1 No. 1 is connected to normally open contacts 6 and 5 of relay 14X of general equipment A via normally closed contacts 4 and 5 of emergency switching relay 8X to supply power to general equipment A, normally open contacts 2 and 3 of relay 30X of general equipment B to supply power to general equipment B, and normally open contacts 3 and 2 of relay 12X of general equipment C to supply power to general equipment C.

[0027] Furthermore, when at least one of the third switch, the fourth switch, and the fifth switch is turned on, the corresponding important equipment A relay 10X or the important equipment B relay 7X or the important equipment C relay 15X) or the important equipment D relay 13X works, and the remote control lines 9 and 10 of the No. 2 static inverter change from the "closed" state to the "open" state, and the No. 2 static inverter outputs 115V / 400Hz single-phase AC power through pin 1.

[0028] Furthermore, pin 1 of static converter X2 No. 2 is connected to the normally open contacts 2 and 3 of relay 10X of important equipment A via the normally closed contacts 1 and 2 of emergency switching relay 8X to power important equipment A, the normally open contacts 2 and 3 of relay 7X of important equipment B to power important equipment B, the normally open contacts 3 and 2 of relay 15X of important equipment C to power important equipment C, and the normally open contacts 3 and 2 of relay 13X of important equipment D to power important equipment D.

[0029] Among them, No. 1 static converter X1 is DL-1000N;

[0030] No. 2 static converter X2 is DL-1000N;

[0031] No. 1 converter fault relay 5X is 2JT5-2 / Ⅱ28C;

[0032] Emergency power supply transfer relay 6X is 2JGXM-2 / Ⅱ28B;

[0033] Important equipment B relay 7X is 2JT5-2 / Ⅱ28C;

[0034] Emergency power supply transfer relay 8X is 2JGXM-2 / Ⅱ28B;

[0035] No. 2 converter fault signal relay 9X is 4JL2-1 / Ⅱ28C;

[0036] Generally, the C relay 12X of the equipment is 2JS15-1 / A, i.e. 3-second B type;

[0037] Important equipment D relay 13X is 2JS15-1 / A grade 3 seconds B type;

[0038] Generally, the relay 14X of equipment A is 2JT5-2 / Ⅱ28C;

[0039] Important equipment C relay 15X is 2JT5-2 / Ⅱ28D;

[0040] Generally, the equipment B relay 30X is 2JT5-2 / Ⅱ28C.

[0041] The beneficial effects of this application are:

[0042] The principle of the present invention is simple and clear, and the implementation is convenient and feasible. By adding an inverter fault signal relay, an emergency conversion relay, a power control relay and a switch for each electrical equipment, the on-off, fault alarm and fault emergency conversion between the secondary power supply and each electrical equipment can be realized. The aircraft has been used, verified and tested, which shows that the design principle is reliable and effective. It can ensure the power supply of important electrical equipment in the event of a fault in the No. 1 or No. 2 inverter of the aircraft, improve the reliability and safety of the secondary power supply, and is of great significance to flight safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Figure 1 Define the diagram for the static converter interface,

[0044] Figure 2 It is the circuit logic relationship diagram. DETAILED DESCRIPTION

[0045] In order to make the purpose, technical scheme and advantages of the implementation of the present invention clearer, the technical scheme in the embodiment of the present invention will be described in more detail in combination with the embodiment of the present invention. In the example, the same or similar reference numerals throughout represent the same or similar originals or elements with the same or similar functions. The described embodiments are part of the embodiments of the present invention, not all of them. The embodiments described below by reference are exemplary and intended to be used to explain the present invention, and should not be construed as limitations on the present invention. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present invention. The following is a detailed description in combination with the embodiments of the present invention.

[0046] The present invention completes the secondary power supply to the aircraft electrical system, fault alarm and emergency conversion by designing two single-phase static converters, two converter fault signal relays, an emergency conversion relay, a power control relay for electrical equipment, a switch and a bus bar. When the 9th and 10th pins of the static converter are turned on, both static converters are in standby state. When at least one device switch under the static converter is turned on, the power control relay for the electrical equipment works, the 9th and 10th pins of the static converter are disconnected, and the static converter converts the 28.5V direct current on the aircraft into 115V / 400Hz single-phase alternating current, and outputs the alternating current through the 1st pin of the static converter to supply power to the corresponding electrical equipment on the aircraft. When the No. 1 converter fails, the converter fault signal relay sends a fault signal to the on-board alarm system when receiving the fault signal sent by the 7th pin of the static converter. When the No. 2 converter fails, a fault signal is sent and the emergency conversion relay (8X) works. When the No. 2 static converter fails through the emergency conversion relay, the system automatically switches the important equipment carried by the No. 2 static converter to be powered by the No. 1 static converter, and cuts off the power supply to the general electrical equipment under the No. 1 static converter.

[0047] like Figure 1 As shown, the 3rd and 6th pins of the No. 1 and No. 2 static converters 1X and 2X input 28V DC, the 8th pin is grounded, the 7th pin outputs a fault signal, and the 9th and 10th pins are connected, and the two static converters are in standby state. When the remote control line 9 and 10 pins of the static converter change from the "closed" state to the "disconnected" state, the static converter outputs 115V / 400Hz single-phase AC power through the 1st and 2nd pins.

[0048] 1) Normal power supply principle

[0049] like Figure 2As shown, under normal circumstances, the No. 1 static converter fault signal relay (5X), emergency conversion relay (8X), and No. 2 converter fault signal relay (9X) do not work, and the emergency power conversion relay (6X) works. The 9th and 10th holes of the No. 1 static converter form a circuit through the 5th contact of the 6X relay, the normally closed contact 1-2 contacts of the 14X relay, the normally closed contact 4-5 contacts of the 30X relay, the normally closed contact 4-5 contacts of the 12X relay, and the 4th contact of the 6X relay; the 9th and 10th holes of the No. 2 static converter form a circuit through the normally closed contact 5-4 contacts of the 10X relay, the normally closed contact 5-4 contacts of the 7X relay, the normally closed contact 5-4 contacts of the 15X relay, and the normally closed contact 5-4 contacts of the 13X relay; Static converters No. 1 and No. 2 are both in standby mode.

[0050] When at least one of switch 1 (1P) and switch 2 (2P) is turned on, the corresponding general equipment A relay (14X) or general equipment B relay (30X) or general equipment C relay (12X) works, and the remote control line 9 and 10 pins of the No. 1 static converter change from the "closed" state to the "opened" state, and the No. 1 static converter outputs 115V / 400Hz single-phase AC power through pin 1. Pin 1 of the No. 1 static converter is connected to the normally open contacts 6 and 5 of the general equipment A relay (14X) through the normally closed contacts 4 and 5 of the emergency conversion relay (8X) to supply power to the general equipment A, the normally open contacts 2 and 3 of the general equipment B relay (30X) to supply power to the general equipment B, and the normally open contacts 3 and 2 of the general equipment C relay (12X) to supply power to the general equipment C.

[0051] When at least one of switch 3 (3P), switch 4 (4P), and switch 5 (5P) is turned on, the corresponding relay (10X) of important equipment A, relay (7X) of important equipment B, relay (15X) of important equipment C, or relay (13X) of important equipment D works, and the remote control line pins 9 and 10 of the No. 2 static converter change from the "closed" state to the "opened" state, and the No. 2 static converter outputs 115V / 400Hz single-phase AC power through pin 1. Pin 1 of the No. 2 static converter is connected to the normally open contacts 2 and 3 of the relay (10X) of the important equipment A through the normally closed contacts 1 and 2 of the emergency conversion relay (8X) to supply power to the important equipment A, the normally open contacts 2 and 3 of the relay (7X) of the important equipment B to supply power to the important equipment B, the normally open contacts 3 and 2 of the relay (15X) of the important equipment C to supply power to the important equipment C, and the normally open contacts 3 and 2 of the relay (13X) of the important equipment D to supply power to the important equipment D.

[0052] 2) Power supply control principle when No. 2 static converter fails

[0053] Static inverter No. 1 serves as a backup for static inverter No. 2. When static inverter No. 2 fails, pin 7 of static inverter No. 2 outputs a ground signal to pin B of inverter No. 2 fault signal relay (9X), and inverter No. 2 fault signal relay (9X) works to output inverter No. 2 fault signal to the onboard integrated alarm system.

[0054] After the No. 2 converter fault signal relay (9X) operates, the 28V DC power of the bus (10P) is transmitted through the 5 and 6 contacts of the No. 2 converter fault signal relay (9X) to the contact A of the emergency conversion relay (8X). The emergency conversion relay (8X) operates, and the 4-5 contacts of 8X are disconnected, cutting off the power supply line from the No. 1 static converter to general equipment A, general equipment B, and general equipment C. At the same time, the 1-2 contacts of 8X are disconnected, and the 2-3 contacts are connected, cutting off the power supply line from the No. 2 static converter to important equipment A, important equipment B, important equipment C, and important equipment D, and the No. 1 static converter supplies power to important equipment A, important equipment B, important equipment C, and important equipment D instead. The line for the No. 1 static converter (1X) to supply power to important equipment is: Pin 1 of the No. 1 static converter (1X) → Pins 2 and 3 of the emergency power supply conversion relay (6X) → Pins 3 and 2 of the emergency conversion relay (8X) → Pins 2 and 3 of each important equipment relay → electrical equipment.

[0055] 3) Power supply control principle when No. 1 static converter fails

[0056] When the No. 1 static converter fails, the No. 1 converter fault signal relay (5X) operates to output the No. 1 converter fault signal to the onboard integrated alarm system.

[0057] In summary, the present invention can realize the secondary power supply to the aircraft electrical system and has a fault alarm function, which can meet the demand for secondary power supply of the aircraft, and can realize emergency conversion when the converter fails, thereby ensuring the power demand of important electrical equipment on board and improving the reliability and safety of the system.

[0058] It is understood by those skilled in the art that, unless otherwise defined, all terms (including technical terms and scientific terms) used herein have the same meaning as the general understanding of ordinary technicians in the field to which the present invention belongs. It should also be understood that terms such as those defined in general dictionaries should be understood to have the same meaning as in the context of the prior art, and unless defined as here, will not be interpreted with idealized or overly formal meanings. The specific implementation methods described above further describe the purpose, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the present invention. Within the spirit and principle of the present invention, any technician familiar with the profession may use the above disclosed technical content to change or modify it into an equivalent embodiment of equivalent changes for application in other fields, but any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the technical solution content of the present invention, any modification, equivalent replacement, improvement, etc., made according to the technical essence of the present invention, should be included in the protection scope of the present invention.

Claims

1. An aircraft secondary power supply control circuit with emergency conversion function, characterized in that: Including No. 1 static converter X1, No. 2 static converter X2, No. 1 converter fault relay 5X, emergency power supply transfer relay 6X, important equipment B relay 7X, emergency power supply transfer relay 8X, No. 2 converter fault signal relay 9X, important equipment A relay 10X, general equipment C relay 12X, important equipment D relay 13X, general equipment A relay 14X, important equipment C relay 15X, general equipment B relay 30X; The direct current on the first bus is respectively connected to the A contact on the No. 1 converter fault relay 5X and the 3 contact on the No. 1 static converter X1; the A contact on the No. 1 converter fault relay 5X is connected to the 5 contact, the B contact of the No. 1 converter fault relay 5X is connected to the 7 contact of the No. 1 static converter X1, and the 2 contact and the 8 contact on the No. 1 static converter X1 are grounded; the No. 1 contact on the No. 1 static converter X1 is connected to the No. 2 contact of the emergency power supply transfer relay 6X, the No. 9 contact of the No. 1 static converter X1 is connected to the No. 4 contact of the emergency power supply transfer relay 6X, and the No. 10 contact of the No. 1 static converter X1 is connected to the No. 5 contact of the emergency power supply transfer relay 6X; The A contact of the emergency power supply transfer relay 6X is connected to the power supply, the B contact is grounded, the 5 contact is connected to the 1 contact of the general equipment A relay 14X, the 4 contact is connected to the 5 contact of the general equipment C relay 12X, the 3 contact is connected to the 3 contact of the emergency power supply transfer relay 8X, and the 2 contact is connected to the 5 contact of the emergency power supply transfer relay 8X; The A contact of the general equipment A relay 14X is connected to the second bus bar after passing through the first switch, the B contact is grounded, the 2 contact is connected to the 5 contact of the general equipment B relay 30X, the 6 contact is connected to the 4 contact of the emergency power supply conversion relay 8X in one way, and the 2 contact of the general equipment B relay 30X in the other way, and the 5 contact is connected to the general equipment A; The A contact of the general device B relay 30X is connected to the second bus bar through the second switch, the B contact is grounded, the 4 contact is connected to the 4 contact of the general device C relay 12X, the 2 contact is connected to the 3 contact of the general device C relay 12X, and the 3 contact is connected to the general device B; The A contact of the general equipment C relay 12X is connected to the first switch, the B contact is grounded, the 5 contact is connected to the 4 contact of the emergency power supply switching relay 6X, and the 2 contact is connected to the general equipment C; Contact 1 of No. 2 static converter X2 is connected to contact 1 of emergency power supply transfer relay 8X, contact 2 is grounded, contact 3 is connected to the first bus, contact 6 is connected to the first bus, contact 7 is connected to contact B of No. 2 converter fault signal relay 9X, contact 8 is grounded, contact 9 is connected to contact 4 of important equipment D relay 13X, and contact 10 is connected to contact 5 of important equipment A relay 10X; The A contact of the emergency power supply transfer relay 8X is connected to the 6 contact of the No. 2 converter fault signal relay 9X, the B contact is grounded, and the 2 contact is connected to the 2 contact of the important equipment A relay 10X; The A contact of the No. 2 converter fault signal relay 9X is connected to the first bus bar, the A contact is connected to the 8 contact, and the 8 contact is connected to the 5 contact; The A contact of the important equipment A relay 10X is connected to the third bus bar after passing through the third switch, the B contact is grounded, the 4 contact is connected to the 5 contact of the important equipment B relay 7X, the 2 contact is connected to the 2 contact of the important equipment B relay 7X, and the 3 contact is connected to the important equipment A; The A contact of the important equipment B relay 7X is connected to the third bus bar after passing through the fourth switch, the B contact is grounded, the 4 contact is connected to the 4 contact of the important equipment C relay 15X, the 2 contact is connected to the 2 contact of the important equipment C relay 15X, and the 3 contact is connected to the important equipment B; The A contact of the important equipment C relay 15X is connected to the third rear bar after passing through the fifth switch, and the B contact is grounded, and the B contact of the important equipment D relay 13X is connected in parallel. The 4 contact is connected to the 5 contact of the important equipment D relay 13X, the 2 contact is connected to the 2 contact of the important equipment D relay 13X; the 3 contact is connected to the important equipment C Contact A of relay 13X of important equipment D is connected to the third bus bar through the fifth switch, and contact 3 is connected to important equipment D.

2. The circuit according to claim 1, characterized in that When the 9th and 10th pins of the No. 1 static converter X1 are turned on, both static converters are in standby state. When the first or second switch under the No. 1 static converter X1 is turned on, the power control relay of the electrical equipment works.

3. The circuit according to claim 2, characterized in that Pins 9 and 10 of No. 1 static converter X1 are disconnected, and No. 1 static converter X1 converts the 28.5V DC power on the aircraft into 115V / 400Hz single-phase AC power, and outputs the AC power through pin 1 of the static converter to supply power to the corresponding electrical equipment on the aircraft.

4. The circuit according to claim 3, characterized in that When the No. 1 static converter X1 fails, the converter fault signal relay receives the fault signal from the 7th foot of the No. 1 static converter X1 and sends a fault signal to the onboard warning system.

5. The circuit according to claim 4, characterized in that When the No. 2 static converter X2 fails, a fault signal is issued and the emergency power conversion relay 8X is activated; when the No. 2 static converter X2 fails, the system automatically switches the equipment carried by the No. 2 static converter X2 to the power supply of the No. 1 static converter X1 through the emergency power conversion relay 8X, and at the same time cuts off the power supply to the general electrical equipment under the No. 1 static converter X1.

6. The circuit according to claim 5, characterized in that When at least one of the first switch 1 and the second switch 2 is turned on, the corresponding general device A relay 14X or the general device B relay 30X or the general device C relay 12X works, and the remote control line 9 and 10 pins of the No. 1 static converter X1 change from the "closed" state to the "open" state, and the No. 1 static converter X1 outputs 115V / 400Hz single-phase AC power through pin 1.

7. The circuit according to claim 6, characterized in that Pin 1 of static converter X1 No. 1 is connected to normally open contacts 6 and 5 of relay 14X of general equipment A via normally closed contacts 4 and 5 of emergency switching relay 8X to supply power to general equipment A, normally open contacts 2 and 3 of relay 30X of general equipment B to supply power to general equipment B, and normally open contacts 3 and 2 of relay 12X of general equipment C to supply power to general equipment C.

8. The circuit according to claim 7, characterized in that When at least one of the third switch, the fourth switch, and the fifth switch is turned on, the corresponding important equipment A relay 10X or the important equipment B relay 7X or the important equipment C relay 15X) or the important equipment D relay 13X works, and the remote control line 9 and 10 pins of the No. 2 static converter change from the "closed" state to the "open" state, and the No. 2 static converter outputs 115V / 400Hz single-phase AC power through pin 1.

9. The circuit according to claim 8, characterized in that Pin 1 of No. 2 static converter X2 is connected to the normally closed contacts 1 and 2 of the emergency conversion relay 8X to the normally open contacts 2 and 3 of the relay 10X of important equipment A to power important equipment A, the normally open contacts 2 and 3 of the relay 7X of important equipment B to power important equipment B, the normally open contacts 3 and 2 of the relay 15X of important equipment C to power important equipment C, and the normally open contacts 3 and 2 of the relay 13X of important equipment D to power important equipment D.

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